Part a) If a rocket, initially at rest, is to attain a terminal velocity (relative to the stars and when the fuel is all burnt up) of a magnitude that happens to equal the magnitude of the exhaust velocity (which is fixed relative to the rocket), what fraction of the initial mass must be fuel? Hint: Examine the situation when we have reached v = u.

Part b) Can a rocket go faster than this terminal velocity? What is its limit?

Part c ) Describe the motion of the overall original system CM, starting from the initial moment (when the rocket first began to blast off) to the attained final velocity in part a.

2. Relevant equations

Given above.

3. The attempt at a solution

Part a) The inital speed is zero, and u equals the final speed so:

[tex] v - 0 = v ln \frac{M_0}{M} [/tex]

[tex] 1 = ln \frac{M_0}{M} [/tex]

Take the exponential of boths sides:

[tex] e = \frac{M_0}{M} [/tex]

I'm not sure if the question is asking for the ratio of the inital mass to the final mass, or if it's asking what the inital mass must be in terms of the final mass...

Part b) The hint given is: What we mean is given that you had no
constraint on the fraction of the rocket that can be used for fuel, is there
an upper limit on the final speed you can the rocket up to?

I have no idea on how to find this. I haven't tried to tackle part c yet because I don't have a handle on parts a and b.

I'm not sure if the question is asking for the ratio of the inital mass to the final mass, or if it's asking what the inital mass must be in terms of the final mass...

Neither of those.

Your lack of understanding lies in not delving into the meaning of these two masses. You are given that all of the fuel has been exhausted at the end. The final mass [itex]M=M_v[/itex] is the mass of the empty vehicle and the payload. At the start, the rocket was loaded with fuel. The initial mass is just the final mass plus the initial fuel load, [itex]M_0=M_v+M_{f_\mathrm{init}}[/itex].

For part a, you are asked "what fraction of the initial mass must be fuel". If you represent the initial mass as I suggested you should be able to answer the question at hand.

Part b) The hint given is: What we mean is given that you had no
constraint on the fraction of the rocket that can be used for fuel, is there
an upper limit on the final speed you can the rocket up to?

I have no idea on how to find this. I haven't tried to tackle part c yet because I don't have a handle on parts a and b.

Any help is appreciated.

What does the hint mean in terms of [itex]M_{f_\mathrm{init}}[/itex]? What does that mean in terms of the final velocity?

Your lack of understanding lies in not delving into the meaning of these two masses. You are given that all of the fuel has been exhausted at the end. The final mass [itex]M=M_v[/itex] is the mass of the empty vehicle and the payload. At the start, the rocket was loaded with fuel. The initial mass is just the final mass plus the initial fuel load, [itex]M_0=M_v+M_{f_\mathrm{init}}[/itex].

For part a, you are asked "what fraction of the initial mass must be fuel". If you represent the initial mass as I suggested you should be able to answer the question at hand.

Hmmm I don't know where I got the equation above, I must have been a bit tired last night. (Edit: I do know, I tried to solve for [tex] M_{final} / M_0 [/tex] instead of [tex] M_{fuel} / M_0 [/tex]).This is my reasoning: